An experimental study on NACA0012 airfoils at transonic speeds has been conducted in order to acquire aerodynamic data for evaluating sidewall boundary-layer effects. Measurements primarily consisted of static pressure on the airfoil and drag force coefficients determined using the wake rake. The tests were performed at free-stream Mach numbers from approximately 0.65 to 0.8, at angles of attack from -2.00 to 2.00, and at Reynolds numbers (based on airfoil chord) from 7*106 to 40 * 106. Mach number corrections for sidewall boundary-layer effects were made, and tests were subsequently performed on two different chord airfoils to confirm the applicability of the correction to different airfoil aspect ratios. This is a supplementary report and presents both uncorrected and corrected data which enables comparative studies to be conducted using computational fluid dynamics and other wind tunnel experimental results.
NACA0012 Airfoil Data Corrected for Sidewall Boundary-layer Effects in the NAL Two-Dimensional Transonic Wind Tunnel
naltm0640t.pdf
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